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GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL (goe320-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL (goe320-il)
Reynolds number: 500,000
Max Cl/Cd: 89.23 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe320-il-500000.txt
Download as CSV file: xf-goe320-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1179   0.09097   0.08788  -0.0450   0.7747   0.0288
  -7.750  -0.1096   0.08809   0.08500  -0.0469   0.7692   0.0294
  -7.500  -0.1073   0.08450   0.08142  -0.0527   0.7630   0.0301
  -7.250  -0.1010   0.08006   0.07692  -0.0625   0.7575   0.0302
  -7.000  -0.0895   0.07714   0.07398  -0.0620   0.7529   0.0304
  -6.750  -0.0758   0.07458   0.07144  -0.0618   0.7479   0.0305
  -6.500  -0.0614   0.07199   0.06883  -0.0630   0.7427   0.0307
  -6.250  -0.0460   0.06935   0.06614  -0.0651   0.7375   0.0309
  -6.000  -0.0288   0.06660   0.06337  -0.0679   0.7324   0.0312
  -5.750  -0.0100   0.06370   0.06046  -0.0712   0.7274   0.0317
  -5.500   0.0105   0.06071   0.05741  -0.0747   0.7230   0.0322
  -5.250   0.0520   0.05424   0.05064  -0.0880   0.7190   0.0342
  -5.000   0.0687   0.05134   0.04771  -0.0887   0.7148   0.0344
  -4.750   0.0881   0.04919   0.04558  -0.0892   0.7101   0.0346
  -4.500   0.1094   0.04713   0.04349  -0.0902   0.7057   0.0349
  -4.250   0.1328   0.04501   0.04129  -0.0915   0.7012   0.0354
  -4.000   0.1582   0.04276   0.03894  -0.0932   0.6965   0.0361
  -3.750   0.1991   0.03769   0.03346  -0.0981   0.6920   0.0388
  -3.500   0.2211   0.03577   0.03153  -0.0986   0.6863   0.0390
  -3.250   0.2448   0.03424   0.02991  -0.0990   0.6802   0.0393
  -3.000   0.2704   0.03268   0.02832  -0.0997   0.6737   0.0399
  -2.750   0.3075   0.02959   0.02471  -0.1009   0.6681   0.0436
  -2.500   0.3312   0.02777   0.02286  -0.1014   0.6620   0.0440
  -2.250   0.3571   0.02649   0.02158  -0.1018   0.6555   0.0444
  -2.000   0.3840   0.02534   0.02035  -0.1022   0.6492   0.0452
  -1.750   0.4167   0.02308   0.01760  -0.1023   0.6436   0.0495
  -1.500   0.4434   0.02186   0.01642  -0.1027   0.6364   0.0500
  -1.250   0.4707   0.02099   0.01548  -0.1029   0.6293   0.0509
  -1.000   0.5019   0.01970   0.01378  -0.1028   0.6224   0.0559
  -0.750   0.5292   0.01861   0.01269  -0.1030   0.6132   0.0567
  -0.500   0.5571   0.01792   0.01195  -0.1031   0.6030   0.0580
  -0.250   0.5901   0.01425   0.00739  -0.1022   0.5933   0.0434
   0.000   0.6185   0.01337   0.00639  -0.1021   0.5795   0.0432
   0.250   0.6466   0.01287   0.00572  -0.1019   0.5600   0.0434
   0.500   0.6737   0.01243   0.00510  -0.1015   0.5283   0.0438
   0.750   0.6974   0.01242   0.00477  -0.1008   0.4603   0.0447
   1.000   0.7207   0.01277   0.00484  -0.1002   0.4087   0.0461
   1.250   0.7459   0.01291   0.00480  -0.0997   0.3841   0.0475
   1.750   0.7987   0.01284   0.00456  -0.0991   0.3585   0.0501
   2.000   0.8249   0.01291   0.00459  -0.0988   0.3496   0.0522
   2.250   0.8522   0.01293   0.00460  -0.0987   0.3431   0.0550
   2.500   0.8788   0.01295   0.00462  -0.0985   0.3365   0.0593
   2.750   0.9051   0.01304   0.00467  -0.0982   0.3304   0.0646
   3.000   0.9325   0.01305   0.00472  -0.0981   0.3255   0.0740
   3.250   0.9592   0.01310   0.00484  -0.0979   0.3202   0.1017
   3.500   0.9820   0.01155   0.00517  -0.0973   0.3150   1.0000
   3.750   1.0086   0.01175   0.00530  -0.0971   0.3103   1.0000
   4.000   1.0352   0.01193   0.00543  -0.0969   0.3052   1.0000
   4.250   1.0608   0.01218   0.00559  -0.0965   0.2996   1.0000
   4.500   1.0862   0.01245   0.00579  -0.0961   0.2941   1.0000
   4.750   1.1127   0.01261   0.00594  -0.0960   0.2887   1.0000
   5.000   1.1380   0.01285   0.00612  -0.0956   0.2825   1.0000
   5.250   1.1628   0.01312   0.00634  -0.0951   0.2764   1.0000
   5.500   1.1886   0.01332   0.00652  -0.0948   0.2694   1.0000
   5.750   1.2121   0.01365   0.00676  -0.0942   0.2612   1.0000
   6.000   1.2372   0.01387   0.00696  -0.0939   0.2522   1.0000
   6.250   1.2602   0.01421   0.00723  -0.0932   0.2420   1.0000
   6.500   1.2820   0.01461   0.00754  -0.0924   0.2304   1.0000
   6.750   1.3040   0.01499   0.00786  -0.0915   0.2201   1.0000
   7.000   1.3244   0.01544   0.00824  -0.0905   0.2120   1.0000
   7.250   1.3443   0.01589   0.00864  -0.0894   0.2056   1.0000
   7.500   1.3620   0.01642   0.00911  -0.0879   0.2005   1.0000
   7.750   1.3802   0.01682   0.00952  -0.0865   0.1975   1.0000
   8.000   1.3972   0.01730   0.01000  -0.0849   0.1946   1.0000
   8.250   1.4133   0.01785   0.01055  -0.0833   0.1921   1.0000
   8.500   1.4287   0.01848   0.01116  -0.0817   0.1897   1.0000
   8.750   1.4429   0.01922   0.01188  -0.0801   0.1874   1.0000
   9.000   1.4598   0.01983   0.01253  -0.0788   0.1860   1.0000
   9.250   1.4773   0.02043   0.01317  -0.0777   0.1849   1.0000
   9.500   1.4943   0.02107   0.01385  -0.0766   0.1837   1.0000
   9.750   1.5109   0.02176   0.01457  -0.0756   0.1826   1.0000
  10.000   1.5272   0.02249   0.01535  -0.0745   0.1813   1.0000
  10.250   1.5429   0.02327   0.01615  -0.0734   0.1800   1.0000
  10.500   1.5581   0.02411   0.01701  -0.0724   0.1788   1.0000
  10.750   1.5728   0.02499   0.01791  -0.0713   0.1778   1.0000
  11.000   1.5873   0.02590   0.01885  -0.0703   0.1768   1.0000
  11.250   1.6013   0.02685   0.01983  -0.0692   0.1758   1.0000
  11.500   1.6154   0.02781   0.02081  -0.0681   0.1747   1.0000
  11.750   1.6295   0.02878   0.02179  -0.0669   0.1736   1.0000
  12.000   1.6444   0.02968   0.02274  -0.0660   0.1727   1.0000
  12.250   1.6595   0.03057   0.02371  -0.0652   0.1718   1.0000
  12.500   1.6737   0.03152   0.02474  -0.0645   0.1705   1.0000
  12.750   1.6875   0.03252   0.02581  -0.0637   0.1692   1.0000
  13.000   1.7007   0.03356   0.02691  -0.0629   0.1680   1.0000
  13.250   1.7137   0.03463   0.02803  -0.0621   0.1667   1.0000
  13.500   1.7259   0.03576   0.02921  -0.0612   0.1655   1.0000
  13.750   1.7376   0.03693   0.03043  -0.0604   0.1642   1.0000
  14.000   1.7488   0.03815   0.03168  -0.0595   0.1630   1.0000
  14.250   1.7602   0.03933   0.03289  -0.0586   0.1617   1.0000
  14.500   1.7736   0.04035   0.03389  -0.0575   0.1597   1.0000
  14.750   1.7825   0.04179   0.03546  -0.0569   0.1586   1.0000
  15.000   1.7906   0.04336   0.03714  -0.0563   0.1574   1.0000
  15.250   1.7990   0.04494   0.03883  -0.0558   0.1560   1.0000
  15.500   1.8075   0.04653   0.04050  -0.0553   0.1545   1.0000
  15.750   1.8157   0.04818   0.04223  -0.0548   0.1530   1.0000
  16.000   1.8236   0.04987   0.04398  -0.0544   0.1516   1.0000
  16.250   1.8301   0.05173   0.04590  -0.0540   0.1500   1.0000
  16.500   1.8365   0.05353   0.04772  -0.0535   0.1482   1.0000
  16.750   1.8442   0.05512   0.04934  -0.0527   0.1462   1.0000
  17.000   1.8484   0.05744   0.05180  -0.0527   0.1452   1.0000
  17.250   1.8523   0.05983   0.05434  -0.0528   0.1438   1.0000
  17.500   1.8558   0.06229   0.05691  -0.0529   0.1419   1.0000
  17.750   1.8592   0.06480   0.05952  -0.0531   0.1399   1.0000
  18.000   1.8610   0.06751   0.06230  -0.0533   0.1378   1.0000
  18.250   1.8595   0.07057   0.06539  -0.0535   0.1353   1.0000
  18.500   1.8595   0.07358   0.06851  -0.0538   0.1331   1.0000
  18.750   1.8609   0.07659   0.07169  -0.0544   0.1303   1.0000
  19.000   1.8593   0.07999   0.07520  -0.0550   0.1267   1.0000
  19.250   1.8504   0.08437   0.07961  -0.0559   0.1231   1.0000
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